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公开(公告)号：US12104795B2
公开(公告)日：2024-10-01
申请号：US17664975
申请日：2022-05-25
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Michael A. Benjamin
Abstract: A combustor for a gas turbine includes a combustor liner that has an outer liner and an inner liner. At least one of the outer liner and the inner liner includes (a) an upstream liner section fixedly connected in the combustor, (b) a downstream liner section fixedly connected in the combustor, and (c) a dilution liner section including a movable portion including at least a part of the dilution liner section and having at least one dilution opening therethrough. The movable portion is arranged to translate in an upstream direction and in a downstream direction. At least one actuator is connected to the movable portion of the dilution liner section and controls translational movement of the movable portion in the upstream direction and the downstream direction to adjust a volume of a primary combustion zone within the combustor.
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公开(公告)号：US20240280265A1
公开(公告)日：2024-08-22
申请号：US18452958
申请日：2023-08-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nayan Vinod Patel , Michael A. Benjamin
CPC classification number: F23R3/06 , F23R3/34 , F02C7/22 , F23R3/14 , F23R3/28 , F23R3/346 , F23R3/36
Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustion chamber, a fuel supply fluidly coupled to the combustion chamber, and a fuel nozzle assembly. The fuel nozzle assembly can include an air flow passage and a fuel flow passage.
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公开(公告)号：US20240230100A9
公开(公告)日：2024-07-11
申请号：US18314565
申请日：2023-05-09
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Hiranya Nath , Michael A. Benjamin , Daniel D. Brown , Sibtosh Pal , Joseph Zelina
CPC classification number: F23R3/60 , F02C7/20 , F23R3/06 , F23R2900/00017 , F23R2900/03042
Abstract: A coupling assembly for a turbine engine. The coupling assembly includes a cold side component, a hot side component, and a fastening mechanism. The cold side component and the hot side component together at least partially form a combustion chamber. The fastening mechanism couples the hot side component to the cold side component. The fastening mechanism includes a stud disposed through the cold side component and a cap positioned on the stud. The cap defines a hollow interior and includes one or more first cap cooling holes. The one or more first cap cooling holes operably direct cooling air into the hollow interior such that the hollow interior provides a cushion of air between the combustion chamber and the stud.
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公开(公告)号：US11994071B2
公开(公告)日：2024-05-28
申请号：US17652790
申请日：2022-02-28
Applicant: General Electric Company
Inventor： Hejie Li , Mathew Paul Thariyan , Diana Julieta Méndez Maya , Jorge Omar Mañón Cantú , Brandon W. Miller , Michael A. Benjamin , Brian Devendorf
Abstract: A fuel system including a fuel metering unit, a heat exchanger, a plurality of fuel nozzles, and a coke filtration system. The fuel metering unit is configured to meter a flow of a hydrocarbon fuel. The heat exchanger is fluidly connected to the fuel metering unit. The heat exchanger is configured to heat the hydrocarbon fuel to improve engine performance or efficiency. The plurality of fuel nozzles is fluidly connected to the heat exchanger downstream of the heat exchanger to receive the hydrocarbon fuel heated by the heat exchanger. The coke filtration system includes at least one filter to remove coke particles in the heated fuel. The coke filtration system is located upstream of the plurality of fuel nozzles and directly downstream of the heat exchanger.
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公开(公告)号：US11978934B2
公开(公告)日：2024-05-07
申请号：US17406894
申请日：2021-08-19
Applicant: General Electric Company
Inventor： Honggang Wang , Michael A. Benjamin
IPC: H01M8/04 , H01M8/04701 , H01M8/04858 , H01M8/0662 , H01M8/24
CPC classification number: H01M8/0662 , H01M8/04738 , H01M8/0491 , H01M8/24 , H01M2250/20
Abstract: An integrated fuel cell and combustor assembly, and a related method. The assembly includes a combustor having a combustor geometry and a combustor exit temperature. The assembly further includes multiple fuel cells fluidly coupled to the combustor, the multiple fuel cells being configured to generate a fuel cell power output using fuel and air directed into the multiple fuel cells and to direct a fuel and air exhaust from the multiple fuel cells into the combustor. The multiple fuel cells include multiple fuel cell control groups arranged in a predetermined electrical configuration about the combustor geometry. Each of the multiple fuel cell control groups has an adjustable electrical current bias.
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Patent Agency Ranking
公开(公告)号：US20240044290A1
公开(公告)日：2024-02-08
申请号：US18489736
申请日：2023-10-18
Applicant: General Electric Company
Inventor： Brandon W. Miller , Robert Jon McQuiston , Stefan Joseph Cafaro , Eric Richard Westervelt , Michael A. Benjamin , Joel M. Haynes , Hejie Li
CPC classification number: F02C7/22 , F23R3/28 , F02C9/28 , F02C7/224 , F23R2900/00 , F05D2240/35 , F05D2220/32
Abstract: A gas turbine engine fuel supply system can include a fuel delivery system, a thermal management system, a fuel manifold, and one or more sensors that identify one or more fuel parameters. A fuel control system can be controlled to adjust one or more parameters of the fuel based on data received from the sensors.
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公开(公告)号：US11892165B2
公开(公告)日：2024-02-06
申请号：US17324451
申请日：2021-05-19
Applicant: General Electric Company
Inventor： Hiranya Nath , Michael A. Benjamin , Rajendra Wankhade , Hari Chandra
CPC classification number: F23R3/283 , F02C7/24 , F23R3/286 , F05D2260/231
Abstract: A heat shield for a fuel nozzle of a gas turbine engine combustor. The heat shield includes a radial flange extending in radial and circumferential directions and has an opening therethrough at a radially inward end of the radial flange, and an annular conical wall extending in longitudinal and circumferential directions, the annular conical wall being connected to the radial flange at the radially inward end of the radial flange. The radial flange includes a flange forward side, and a flange aft side, and has a flange outer end portion. The flange outer end portion includes a flange rounded end portion on one of the flange forward side or the flange aft side, and a flange rounded protruding lip on the other of the flange forward side or the flange aft side, the rounded protruding lip extending in the longitudinal direction.
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公开(公告)号：US20230400186A1
公开(公告)日：2023-12-14
申请号：US18450633
申请日：2023-08-16
Applicant: General Electric Company
Inventor： Hari Ravi Chandra , Arvind Kumar Rao , Shai Birmaher , Jayanth Sekar , Gurunath Gandikota , Michael A. Benjamin
CPC classification number: F23R3/343 , F23R3/286 , F02C7/222 , F23D14/70 , F23D14/64 , F23D2206/10 , F05D2240/35
Abstract: A mixing assembly includes a pilot mixer and a main mixer. The main mixer includes a main housing, a fuel manifold positioned between a pilot housing and the main housing, a mixer foot extending outward from a forward end of the main housing, and a main swirler body including a plurality of vanes. The main swirler body surrounds the main housing and defines an annular mixing channel between the main housing and the main swirler body, and being coupled to the mixer foot. An annular main fuel ring extends axially aft from the mixer foot into the annular mixing channel. The mixer foot extends farther from the main housing than the main fuel ring. At least one of the mixer foot or the main fuel ring includes a plurality of fuel injection ports positioned to discharge fuel into a central portion of the annular mixing channel.
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公开(公告)号：US20230399980A1
公开(公告)日：2023-12-14
申请号：US17805986
申请日：2022-06-08
Applicant: General Electric Company
Inventor： Hejie Li , Shai Birmaher , Michael A. Benjamin
Abstract: A gas turbine engine including a combustor, a plurality of fuel nozzles, and at least one fuel manifold. The combustor includes a combustion chamber. The plurality of fuel injects fuel into the combustion chamber of the combustor. The gas turbine engine may include a first fuel circuit and a second fuel circuit. The first fuel circuit includes a first fuel manifold fluidly connected to at least one fuel nozzle of the plurality of fuel nozzles to distribute the fuel to the at least one fuel nozzle at a first temperature. The second fuel circuit includes a second fuel manifold fluidly connected to at least one fuel nozzle of the plurality of fuel nozzles to distribute the fuel to the at least one fuel nozzle at a second. The second temperature is less than the first temperature.
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公开(公告)号：US20230366547A1
公开(公告)日：2023-11-16
申请号：US17932332
申请日：2022-09-15
Applicant: General Electric Company
Inventor： Hiranya Nath , Ravindra Shankar Ganiger , Michael A. Benjamin
IPC: F23R3/00
CPC classification number: F23R3/002 , F23R2900/00014 , F23R2900/03042
Abstract: A hollow plank of a combustor liner defining a combustion chamber including an inner wall having a plurality of inner openings and one or more inner holes, an outer wall having one or more outer openings and a plurality of outer holes, a plurality of lateral walls coupled to the inner wall and the outer wall to define a cavity, and a partition wall connected to the plurality of lateral walls and dividing the cavity into a first sub-cavity and a second sub-cavity. The one or more outer openings communicate with the first sub-cavity and communicate through a plurality of tubes with the second sub-cavity. The plurality of inner openings communicate with the second sub-cavity and communicate with the first sub-cavity through one or more bypass tubes. The first sub-cavity or the second sub-cavity, or both, are frequency tuned to reduce combustion dynamic frequencies.
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